The present invention relates to a reinforcing tip cap for an aerofoil blade. The tip cap comprises a body for attaching to the tip of an aerofoil blade and a plurality of abrading elements fixed in the body for abrading a surface against which the tip cap rubs in use.
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1. A composite aerofoil blade reinforced at its tip with a reinforcing tip cap, the reinforcing tip cap comprising:
a body configured for attaching to the tip of the composite aerofoil blade; and
a plurality of abrading elements fixed in the body configured for abrading a surface against which the reinforcing tip cap rubs in use, wherein
the body is formed of a composite material including a matrix and reinforcing fibers.
9. A method of reinforcing a composite aerofoil blade tip at its tip with a reinforcing tip cap, the method comprising:
attaching to the composite blade tip a reinforcing tip cap having:
a body configured for attaching to the tip of the composite aerofoil blade; and
a plurality of abrading elements fixed in the body configured for abrading a surface against which the reinforcing tip cap rubs in use, wherein
the body is formed of a composite material including a matrix and reinforcing fibers.
2. The tip cap according to
3. The tip cap according to
4. The tip cap according to
5. The tip cap according to
6. The composite aerofoil blade according to
7. The composite aerofoil blade according to
8. An aero engine comprising:
a composite aerofoil blade; and
the reinforcing tip cap according to
the composite aerofoil blade is reinforced with the reinforcing tip cap.
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The present invention relates to a composite aerofoil blade with a wear-resistant tip and to a method of manufacturing the same.
In a ducted fan, such as is commonly used in an aero engine, for example, a fan is disposed co-axially within a duct and is driven to rotate within the duct to direct air rearwardly through the duct.
For efficiency and stability of the fan blades the gaps between the tips of the blades and the inner casing of the duct within which the fan rotates must be kept to a minimum so as to minimise leakage of air around the tips of the blades.
However, with smaller clearances between the blade tips and the duct casing comes the likelihood that some rubbing between the two will take place in certain operating conditions. For example, when the speed of rotation of the fan increases the blades can elongate due to centrifugal forces. Also, for an aero engine, during certain maneuvers of the aircraft gyroscopic forces may temporarily cause the fan and duct to come out of perfect axial alignment which can lead to rubbing of the blade tips against the casing.
To accommodate this rubbing, the duct casing is provided with a lining comprising a sacrificial abradable layer which is designed to be cut or rubbed away by the blade tips. The liner is sometimes referred to as a Fan Track Liner (FTL).
For a metal blade, such as a blade of titanium alloy, this abrasion, and the temperatures of between 700-800° C. which it causes, presents no serious problem. However, in the interests of weight saving, aero engine manufacturers are increasingly looking to composite materials for manufacturing primary components such as fan blades. A composite fan blade typically comprises layers of fabric containing fibres which have high tensile strength, such as carbon fibres, embedded in an epoxy resin matrix. The tip of a blade made of such composite material would not abrade the sacrificial abradable layer in the duct casing. Instead the blade tip itself would become worn down by the rubbing. In any case the epoxy resin would melt at the temperatures generated by the abrasion which could potentially lead to disintegration of the blade.
Attempts have been made to reinforce a composite blade tip using cutting elements of high wear resistance. U.S. Pat. No. 5,112,194 exemplifies such an approach and describes embedding boron rod-like filaments in the composite tip. However, this solution is not without its problems. Firstly, boron rods, though very hard, are brittle and could shatter during the rubbing of the blade tip against the liner material. Also, the process of embedding the rods in the lay-up of the blade could be costly and time consuming. Furthermore, the relatively large diameter of the boron rods, when compared with the fibres within the blade composite, will result in plies being displaced to accommodate the rods. This causes local stress concentrations which act in the weakest direction of the laminate structure and which can degrade blade-tip performance in the event of a bird strike, for example.
Embodiments of the present invention aim to address at least partly the disadvantages of the prior art.
The present invention is defined in the attached independent claims, to which reference should now be made. Further, preferred features may be found in the sub claims appended thereto.
According to the invention there is provided a reinforcing tip cap for an aerofoil blade, comprising a body for attaching to the tip of an aerofoil blade and a plurality of abrading elements fixed in the body for abrading a surface against which the tip cap rubs in use.
Preferably the tip cap is a wear-resistant tip cap which is arranged in use to reinforce the tip of an aerofoil blade against wear.
The body may be arranged to wrap around a tip of an aerofoil blade, and be bonded thereto, such that the abrading elements become disposed at positions along the edge of the tip of the blade in a chordwise extent.
The abrading elements are preferably configured within the body so as to cause maximum abrasion of a surface against which the tip cap rubs in use.
In a preferred arrangement the abrading elements are embedded in the body such that they extend in a spanwise- or Z-direction with respect to the blade in use.
The body may be of a composite material including a matrix and reinforcing fibres.
Preferably the abrading elements comprise at least one of the following: straight pins, crossover pins, bundles of fibres, staples.
At least some of the abrading elements may be embedded in a vibration-damping material.
The invention also includes an aerofoil blade reinforced at its tip with a tip cap according to any statement herein.
The aerofoil blade may be of composite material.
The invention also includes an aero engine having an aerofoil blade reinforced at its tip with a tip cap according to any statement herein.
The invention also includes a method of reinforcing an aerofoil blade tip comprising attaching to the blade tip a tip cap according to any statement herein.
Preferred embodiments of the invention will now be described, by way of example only, with reference to the accompanying diagrammatic drawings, in which:
Turning to
In the interests of efficiency and of stability of the fan blades 16 leakage of air around the tips of the blades 16 should be kept to a minimum. Typically the blades have only a few millimeters of clearance between their tips and the inside surface of the duct casing. A sacrificial layer (not shown) of abradable material forms a liner around the inside of the duct casing.
In accordance with an embodiment of the present invention, in order to avoid damaging the tips of the composite blades as they rub against the abradable liner, the blade tips are protected by a reinforcing cap of highly wear-resistant material as will now be described with reference to
The tip cap 26 is then wrapped around the edge of a composite blade tip 34, as is shown in
The tip caps may be formed predominately of composite material which may be reinforced with carbon, glass or any other appropriate fibres. Beneficially, the cap can be co-bonded to the aerofoil
The wraps can be made from other fibre-reinforced plastics such as glass fibres, aramid fibres, polymeric fibres and natural fibres, and can be combined with appropriate resins known in the art including, but not limited to, thermoplastic or phenolic ones. As an alternative to being co-bonded the cap can be co-cured (i.e. cured as one in the same mould) with the aerofoil or secondary bonded (adhered together after initial curing). Co-curing has the benefit of offering the best possible bond surface as the resin flows between the blade and the wrap which effectively become a single component. Whilst this process is complex and expensive it offers the best mechanical properties. With secondary bonding the protective cap is cured separately and is then bonded to the blade in an extra processing step. The cap can be preformed using tape-laying or hot forming or even a hand layup technique.
Alternatively, metals or plastics can be used for the caps although it may not be viable to co-cure or co-bond them thus adding complexity to the assembly process.
In particular, in the embodiment shown in
In
Other abrading elements could be used such as glass fibre pins, aramid fibre pins, or metal pins, such as of titanium or invar. To resist the build up of heat during rubbing of the tip against the liner, the tip cap 26 can be interleaved with metal foils and/or coated with a metallic coating to dissipate heat away from the tip.
The embodiments of the tip cap described above provide several advantages. In particular, they are inexpensive to manufacture and can be readily repaired or replaced. Also the abrading elements do not compromise the blade tip performance. The elements themselves effectively slice, or cut, through the liner material individually as opposed to rubbing or grinding which would be the case with a continuous tip edge. Accordingly, less heat is generated.
Patent | Priority | Assignee | Title |
10301950, | Mar 15 2013 | RTX CORPORATION | Enhanced protection for aluminum fan blade via sacrificial layer |
10578115, | May 19 2016 | Rolls-Royce plc | Composite component with hollow reinforcing pins |
10794394, | Apr 15 2015 | RTX CORPORATION | Abrasive tip for composite fan blades |
Patent | Priority | Assignee | Title |
1545560, | |||
4411597, | Mar 20 1981 | The United States of America as represented by the Administrator of the | Tip cap for a rotor blade |
4680199, | Mar 21 1986 | United Technologies Corporation | Method for depositing a layer of abrasive material on a substrate |
5024884, | Dec 24 1984 | United Technologies Corporation | Abradable seal having particulate erosion resistance |
5112194, | Oct 18 1990 | United Technologies Corporation | Composite blade having wear resistant tip |
5269658, | Dec 24 1990 | United Technologies Corporation | Composite blade with partial length spar |
5885059, | Dec 23 1996 | Sikorsky Aircraft Corporation | Composite tip cap assembly for a helicopter main rotor blade |
20070099011, | |||
20070147990, | |||
20080159868, | |||
20080175706, | |||
EP1270876, | |||
EP1312760, | |||
FR2683764, | |||
GB1311806, | |||
GB1437236, | |||
WO9202410, |
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